Rain erosion protective device

ABSTRACT

Apparatus for the protection of aerodynamic surfaces from rain erosion whereby a region of high-impact pressure air is trapped ahead of the surface being protected which is operative to disintegrate raindrops prior to their impact upon the surface and including a rupturable static protective means for said device.

United States Patent Nicholson et al.

RAIN EROSION PROTECTIVE DEVICE James E. Nicholson, Sudbury; Richard H. Adams, Bedford, both of Mass.

Sanders Associates, Inc., Nashua, NH.

Aug. 17, 1970 Related US. Application Data Division of Ser. No. 699,465, Jan. 22, 1968, Pat. No. 3,524,608.

Inventors:

Assignee:

Filed:

Appl. No.:

[1.5. Ci. ..244/1 R, 244/121 Int. Cl ..B64d 45/00 Field of Search ..244/ 1 R 1 Jan. 25, i972 {56] References Cited UNITED STATES PATENTS 2,489,984 11/1949 Shoemaker ..244/1 R Primary Examiner--Milton Buchler. Assistant Examiner-Jeffrey L. Forman Attorney-Louis Etlinger 5 7] ABSTRACT Apparatus for the protection of aerodynamic surfaces from rain erosion whereby a region of high-impact pressure air is trapped ahead of the surface being protected which is operative to disintegrate raindrops prior to their impact upon the surface and including a rupturable static protective means for said device.

3 Claims, 4 Drawing Figures PATENIEB Jmzsm sum UF 2 I/VVENTORS JAMES E. NICHOLSON RICHARD H. ADAMS I x B) V A GEN r PATENTED JANZSIBYZ 3,637,166

SHEET 2 BF 2 FIGBA v lNVE/VTOR5 JAMES E. NICHOLSON RICHARD H. ADAMS AGENT RAIN EROSION PROTECTIVE DEVICE BACKGROUND OF THE INVENTION This is a division of our copendingjapplication Ser. No. 699,465, filed Jan. 22, 1968 for Rain Erosion Protective Device now US. Pat. No. 3,524,608. This invention was made in the course of a contract with the Department of the Navy.

The present invention relates generally to aerodynamic devices and more particularly to apparatus for the protection of aerodynamic surfaces from damage by rain erosion. The apparatus of the present invention is particularly suited to provide such protection for vulnerable surfaces (e.g., radomes, IR domes and the like) carried by missiles and aircraft wherein a sensor disposed behind the surface is required to have an unobstructed view when the apparatus is in place.

DESCRIPTION OF THE PRIOR ART Rain erosion of highspeed aerodynamic surfaces has been of concern since the introduction of the first high-speed allweather military aircraft. As aircraft speeds have increased it has become evident that raindrops are capable of totally destroying such surfaces as optical windows and radomes carried by such aircraft. Prior attempts have been made to prevent damage of aerodynamic surfaces by airborne particles, however, these attempts have involved the use of a physical body disposed ahead of the surfaceto be protected and in many cases are limited in their operation to supersonic velocities. Typical of the prior art relating to this type of protective device is US. Pat. No. 3,236,093, which issued to F. D. Werner on Feb. 22, 1966. A physical structure is disposed ahead of the surface to be protected from damage whereby particulate matter in the atmosphere is deflected prior to striking the surface. This solution to the problem of rain erosion clearly precludes the existence of an unobstructed forward field-of-view from the surface being protected.

OBJECTS OF THE INVENTION It is thus a primary object of the present invention to provide a new and novel method and apparatus for the prevention of damage to aerodynamic surfaces by rain erosion which does not obstruct the forward field-of-view from the surface protected thereby.

It is an additional object of the present invention to provide apparatus of the above-described nature which is independent in its operation on the formation of an aerodynamic shock wave.

It is another object of the present invention to provide apparatus of the above-described nature which may be automatically removed at a preselected time in a reliable and predetermined manner.

It is a further object of the present invention to provide a new and novel rain erosion protection device whichreduces the aerodynamic drag of the surface which it protects.

It is yet another object of the present invention to provide a new and novel rain erosion protectiondevice which reduces the aerodynamic heating rate of the surface protected thereby.

These and other objects, features and advantages of the present invention will become more apparent from the detailed discussion considered in conjunction with the accompanying drawings. The scope of the invention will be indicated in the claims.

SUMMARY OF THE INVENTION The present invention forms a chamber about a volume of space ahead of the surface which is to be protected. The forward end of the chamber is open to the surrounding environment and the rearward extremity of the chamber is secured about the surface to be protected. The length of the chamber is determined according to the density of the surrounding environment, the speed at which the surface moves and the diameter of the particulate matter to be disintegrated. As the vehicle moves through the atmosphere ram air is admitted to the chamber through its open forward end. Thus a region of high-impact pressure air which is substantially at rest with respect to the surface is trapped within the chamber and moves with the velocity of the vehicle. Particulate matter in the atmosphere which enters the forward end of the device impinges on this region of high-impact pressure air and is thereby disintegrated. The open forward end of the device further permits an unobstructed field of view in the forward direction for any sensor disposed behind the surface being protected. A further advantage of the present invention is that a net improvement in aerodynamicperformance from that of an unprotected surface may be realized.

In one form the apparatus of the present invention may be permanently affixed such that it provides rain erosion protection to a dome or window disposed on an aircraft.

In a further embodiment the apparatus may be mounted to the forward end of a missile or other aerodynamic vehicle such that it may be automatically removed at a preselected time.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. I is a schematic representation of the present invention;

FIG. 2 is a schematic illustration of the manner in which raindrop disintegration is provided;

FIG. 3 is a cross section view of one embodiment of the present invention;

FIG. 3A is an enlarged elevation of one separation control means as applicable to the present invention.

DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to FIG. 1 there is illustrated a schematic representation of the present invention. A parent vehicle 10 such as an aircraft or missile having a surface 12, for example a fiberglass radome glass optical window or a thin metal which is vulnerable to damage by rain erosion, is required to operate through regions of the atmosphere containing concentrations of raindrops 14 or other particulate matter such as dust. The present invention is illustrated as a conical element protective device 16 having an open forward end 18 and mounted at its opposite end 20 to the body of the parent vehicle 10 such that the vulnerable surface I2 is encompassed thereby. The protective device 16 may be fabricated of any material having sufficient structural integrity to withstand the aerodynamic environment such as for example aluminum or a reinforced, injection-molded plastic. As the vehicle moves through the atmosphere in the direction indicated by the arrow 22 ram air enters the forward end of the protective device 16 thus creating a region of high-impact pressure air therein.

This region of air has an impact pressure defined by the ambient atmospheric density and the velocity of the parent vehicle I0 and is carried along by the device 16 at the same velocity as the vehicle 10. Raindrops 14 entering the open forward end 18 of the protective device I6 are impingent upon the aforesaid region of high-impact pressure air and, as will be more fully explained below, are disintegrated thereby into droplets of such small dimension that substantially no damage is incurred by the surface 12. It will be noted that although efficient protection from rain erosion damage is afforded the surface 12 by the protective device 16 an unobstructed forward field-of-view 24 remains available should it be desired to locate sensing apparatus such as radar, infrared or optical receiving system (not shown) behind the surface I2. It will further be noted that the present invention is not limited in its operation to any particular velocity. Rain erosion protection is provided equally well at subsonic, transonic and supersonic velocities since operation is not dependent upon the formation of an aerodynamic shock wave ahead of the vehicle 10.

FIG. 2 presents an expanded schematic illustration of the manner in which the present invention provides for the disintegration of raindrops 14 which, if permitted to impact directly on the surface being protected, would cause extensive erosion damage. The present invention 16 creates a region of air ahead of the surface to be protected of a high-impact pressure P which is greater than the ambient pressure of the atmosphere P Thus raindrops l4 entering the protective device 16 are subjected to a sudden impact with the high-pressure air. Upon entry into the device 16 the drop begins to flatten into a disc-shaped configuration 14a. As the breakup proceeds the drop continues to flatten until the forces on the drop 14b exceeds its surface tension and tiny droplets of water 26 are stripped away from the disc. The droplets 26 in actual practice form an aerosol which is substantially harmless to the surface being protected. The physical extent of the region of high-impact pressure required to substantially preclude rain erosion damage has been found to be a function of the density of the high-impact pressure region of ram air created by the protective device [6 and the initial diameter of the raindrop to be disintegrated. These parameters determine the length of the protective device 16 by the relationship S=l(750/d) l/2l2 1d,, (1)

where S is the length of the protective device in inches,

is the ram air density created within the protective device in pounds per cubic foot,

(1,, is the initial diameter of the raindrop in inches, and

750 is a constant of proportionality in units of pounds per cubic foot.

The ram air density is determined for supersonic velocities hy the formula where p,, is the ram air density in pounds per cubic foot,

p,, is the ambient atmospheric density, and

M is the velocity of the surface expressed in Mach No.

For subsonic velocities the ram air density is defined by the relationship Pa P( /2 (a) where the symbols are the same as defined hereinabove for supersonic velocities. It will be noted that equations (2) and (3) for determining the ram air density are equivalent for flight at the speed of sound (i.e., M=l.0) and thus are continuous in their definition of the ram air density created within the protective device 16.

Thus by equations (l) and (3) a protective device having a length of approximately 6.6 inches is adequate to protect an aerodynamic surface moving at 400 feet per second at sea level (M =0.35) from erosion damage by raindrops having initial diameters of approximately 0.079 inch (2 millimeters). In actual practice the length of the protective device is determined for the most extreme conditions of maximum velocity, lowest atmospheric density and largest raindrop diameter expected to be encountered by the surface to be protected in its operating environment. Since the surface to be protected will typically have some intrinsic erosion strength, a length less than that predicted by equation l will generally be adequate to protect the surface. The extent of this reduction from the predicted value will be directly dependent upon the erosion strength of a given surface material.

In addition to the prevention of rain erosion damage the apparatus of the present invention may also provide reduction in both the aerodynamic drag and aerodynamic heating of the surface protected. In many instances the surface to be protected by apparatus of the present invention is a radome, IR dome, optical window or the like. From electronic and optical considerations it is desirable to fabricate such surfaces in a hemispherical configuration; however, aerodynamically this shape is not optimum. The present invention may be constructed in any desired aerodynamically optimized configuration such as for example a cylinder, truncated cone or truncated ogivc and may provide a net reduction in the aerodynamic drag coefficient from that which is characteristic of a hemispherical shape. Further, when the above described surfaces are mounted on high-velocity vehicles aerodynamic heating occurs which may be detrimental to the operation of a sensor disposed behind the surface. Without the present invention the surface could, after sustained high-velocity flight, experience temperatures approaching the stagnation temperature, i.e., the temperature reached at the point at which all of the kinetic energy of the airstream impingent on said surface is converted to thermal energy. Such elevated temperatures are particularly detrimental to the performance of sensors which operate in the infrared region of the electromagnetic spectrum. The present invention displaces the aerodynamic stagnation point away in the forward direction from the surface being protected thus significantly reducing the rate at which the surface is heated without introducing any obstruction into the forward field of view of the sensor.

In FIG. 3 there is shown a more detailed cross-sectional illustration of a further embodiment of the present invention wherein a surface 12 to be protected from rain erosion is shown mounted on a parent vehicle 10 which could be for example a missile or other projectile. In many such applications of the present invention it is desirable to remove the protective device in order to afford a sensor disposed behind the surface 12 a wider field-of-view than would be available with the protective device in place. The protective device 16 together with a circumferential mounting and deployment apparatus 28 is shown. This embodiment of the invention provides for the automatic release and separation of the protective device at some preselected time, such as at the time a missile or projectile 10 is released from an aircraft. The mounting and deployment apparatus 28 is illustrated as having an annular configuration; however, in actual practice the configuration and dimension will be determined by the parent vehicle 10 struc ture, and may be secured thereto by any convenient means such as adhesives, bolts or the like. The protective device 16 is coupled to the mounting and deployment apparatus 28 by a severable attachment means such as an explosive bolt 30 which is electrically coupled to a deployment activation means 32 which may be disposed either within the mounting apparatus or within the parent vehicle 10. The protective device is further pivotally coupled at a position 34 substantially opposite the above described severable attachment means 30. This pivotal coupling 34 provides for the predictable separation of the protective device 16 from the mounting and deployment apparatus,28 in the manner described below. Also illustrated in FIG. 3 are water vent apertures 36 disposed about the circumference of the protective device 16 proximate the rearward end thereof. These vents provide for the disposal of water which would otherwise accumulate during sustained flight through rain. It is preferred that the exit area are provided by the vents 36 be less than 10 percent of the area of the open forward end of the protective device 16. in this manner an undesirable accumulation of water is prevented without a significant degradation of the high-impact pressure region created by the protective device. FIG. 3 further illustrates a provision for the protection of the surface 12 from the effects of dust and moisture prior to the time the vehicle 10 becomes airborne. A rupturable membrane 38 may be stretched over the open forward end of the protective device 16 and secured thereto for example by an 0" ring 40. A portion 42 of the forward edge of the protective device 16 may be serrated or otherwise formed to provide a cutting means. The aerodynamic forces developing when the parent vehicle 10 reaches a preselected velocity force the membrane 38 against the cutting means42 thus causing the stretched membrane 38 to be withdrawn from the forward opening in the protective device 16.

The protective device l6 may be automatically removed at any preselected time by severing the attachment means 30. As described above the pressure within the protective device 16 is elevated with respect to the ambient atmospheric pressure thus the device experiences a net force which tends to move it forward with respect to the surface l2. A pivotal attachment means indicated generally at 34 in H6. 3 is illustrated in greater detail in FIG. 3A. At least one projection 44 is provided in the annular mounting and deployment means 28 (partially shown). The projection 44 has a rod shaped member 46 disposed therethrough. A portion of the rearward facing edge of the protection device 16 may be formed in a configuration which is most clearly analogous to that ofa J hinge. Thus as the protective device 16 moves away from the surface 12, it rotates downward about the rod-shaped member 46 of the pivotal attachment means 34 and complete separation is prevented until the device has rotated sufficiently far to be carried away by the airstream without hazard to the parent vehicle 10. It will be obvious to one skilled in the art that the above-described pivotal attachment means is only one of many solutions to the pivotal attachment problem which would work equally well.

It will thus be seen that the objects set forth above, among those made apparent from the preceeding description are efficiently attained and since certain changes may be made in the above construction without departing from the scope of the invention, it is intended that all matter contained in the above description as shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense.

It is also to be understood that the following claims are intended to cover all of the generic and specific features of the invention therein described and all statements of the scope of the invention, which, as a matter of language, might be said to fall therebetween.

Having described what is new and novel and desired to secure by Letters Patent, what is claimed is:

ll. Improved apparatus for protecting a forward surface of an airborne vehicle from erosion damage by raindrops including means for creating a pressurized region of air ahead of said surface, said region creating means formed as a hollow body of revolution having a forward and open to the atmosphere, said region of pressurized air created thereby being substantially at rest with respect to said surface, of a density and pres sure which is greater than the ambient density and pressure of said atmosphere, and operative to disintegrate said raindrops prior to impact upon said surface, means for coupling a rearward end of said region creating means firmly to said vehicle and about said surface including severable first attachment means comprising an explosive bolt, pivotal second attachment means, and deployment activation means, said first and second attachment means being disposed substantially op posite each other and forming an integral portion of said coupling means, said region creating means being severably coupled to said first attachment means, and pivotally coupled to said second attachment means, and wherein said improvement comprises rupturable static protective means disposed such that said open forward end of said region creating means is covered thereby, attachment means whereby said rupturable static protective means is secured to said region creating means, and cutting means formed in at least a portion of said forward end of said region creating means whereby said rupturable protective means is ruptured when said vehicle moves through said atmosphere at a preselected velocity.

2. Apparatus as recited in claim I wherein said rupturable static protective means. comprises a resilient diaphragm stretched over said open forward end of said region creating means and circumferentially secured to the exterior surface thereof. 3. Apparatus as recited in claim 1 wherein said cutting means comprises a serrated knife edge integrally formed in the leading edge of said region creating means. 

1. Improved apparatus for protecting a forward surface of an airborne vehicle from erosion damage by raindrops including means for creating a pressurized region of air ahead of said surface, said region creating means formed as a hollow body of revolution having a forward end open to the atmosphere, said region of pressurized air created thereby being substantially at rest with respect to said surface, of a density and pressure which is greater than the ambient density and pressure of said atmosphere, and operative to disintegrate said raindrops prior to impact upon said surface, means for coupling a rearward end of said region creating means firmly to said vehicle and about said surface including severable first attachment means comprising an explosive bolt, pivotal second attachment means, and deployment activation means, said first and second attachment means being disposed substantially opposite each other and forming an integral portion of said coupling means, said region creating means being severably coupled to said first attachment means, and pivotally coupled to said second attachment means, and wherein said improvement comprises rupturable static protective means disposed such that said open forward end of said region creating means is covered thereby, attachment means whereby said rupturable static protective means is secured to said region creating means, and cutting means formed in at least a portion of said forward end of said region creating means whereby said rupturable protective means is ruptured when said vehicle moves through said atmosphere at a preselected velocity.
 2. Apparatus as recited in claim 1 wherein said rupturable static protective means comprises a resilient diaphragm stretched over said open forward end of said region creating means and circumferentially secured to the exterior surface thereof.
 3. Apparatus as recited in claim 1 wherein said cutting means comprises a serrated knife edge integrally formed in the leading edge of said region creating means. 